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51. 发明公开

EP3187420A1 AIRCRAFT WITH REAR MOUNTED ENGINES 有权
标题翻译：带后悬式发动机的飞机
公开(公告)号：EP3187420A1
公开(公告)日：2017-07-05
申请号：EP15382681.3
申请日：2015-12-31
申请人： Airbus Operations S.L.
发明人： MARTÍNEZ MUÑOZ, JOSÉ LUIS
IPC分类号： B64D27/02
CPC分类号： B64D27/02 , B64D2027/005 , Y02T50/44 , Y02T50/66
摘要： Aircraft (1, 1') with rear mounted engines (2, 2'), comprising a vertical tail plane (3) and a horizontal tail plane (4), in which the engines (2, 2') are mounted on top of the horizontal tail plane (4), such that the horizontal tail plane (4) comprises an inner fixed part (5) attached to the fuselage (8) of the aircraft (1, 1'), the inner fixed part (5) comprising an elevator (7), and two outer movable parts (6), each one of the outer movable parts (6) being located at each side end of the horizontal tail plane (4) which is furthest away from the fuselage (8) of the aircraft (1, 1'), such that both the inner fixed part (5) and the outer movable parts (6) are at least partially subjected to the flow coming from the engines (2, 2') when they are in use.
摘要翻译：具有后置发动机（2,2'）的飞机（1,1'）包括垂直尾板（3）和水平尾板（4），其中发动机（2,2'）安装在顶部所述水平尾翼（4）使得所述水平尾翼（4）包括附接到所述飞行器（1,1'）的所述机身（8）的内部固定部分（5），所述内部固定部分（5）包括一个升降机（7）和两个外部活动部件（6），每个外部活动部件（6）位于水平尾翼（4）的离机身（8）最远的每个侧端（1,1'），使得内部固定部分（5）和外部活动部分（6）在使用时至少部分地受到来自发动机（2,2'）的流动的影响。

52. 发明授权

EP2760737B1 PALE POUR UNE HELICE DE TURBOMACHINE, NOTAMMENT A SOUFFLANTE NON CARENEE, HELICE ET TURBOMACHINE CORRESPONDANTES 有权转让
标题翻译： PROPELLER片COAT松藩发动机，这样的螺旋桨叶片和风扇电厂螺旋桨
公开(公告)号：EP2760737B1
公开(公告)日：2017-04-19
申请号：EP12775789.6
申请日：2012-09-28
申请人： Safran Aircraft Engines , Onera
发明人： VION, Laurence , DELATTRE, Grégory , JACQUIN, Laurent , RODRIGUEZ, Benoit , BOISARD, Ronan , ORTUN, Biel , FALISSARD, Fabrice
IPC分类号： B64C11/18 , B64C27/467 , F01D5/14
CPC分类号： B64C11/18 , B64C11/48 , B64C2003/148 , B64D2027/005 , F01D5/141 , F01D5/145 , F05D2220/324 , F05D2220/325 , Y02T50/66 , Y02T50/673

53. 发明公开

EP3138771A1 SYSTEM AND METHOD FOR CONTROLLING PROPELLER PITCH 审中-公开
标题翻译：系统VERFAHREN ZUR STEUERUNG DER PROPELLERSTEIGUNG
公开(公告)号：EP3138771A1
公开(公告)日：2017-03-08
申请号：EP16186944.1
申请日：2016-09-02
申请人： General Electric Company
发明人： MISZKIEWICZ, Krzysztof
IPC分类号： B64C11/38
CPC分类号： B64C11/38 , B64C11/306 , B64D2027/005 , F02C3/04 , F02C7/06 , F05D2220/323 , F05D2240/35 , Y02T50/66
摘要： Systems 40 and methods are disclosed for controlling the pitch angle of a propeller and rotor assembly that selectively limit the pitch angle according to a selected mode of operation. The system comprises an actuator 45 having forward and aft chambers 56, 58, an oil transfer bearing (OTB) 70, and a fine stop collar 86. The fine stop collar including a first passage 88 in fluid communication with the OTB and forward chamber during a ground-based mode of operation, and a second fluid passage 90 being in fluid communication with the OTB and forward chamber during a flight-based mode of operation.
摘要翻译：公开了系统40和方法，用于控制螺旋桨和转子组件的俯仰角，其根据所选择的操作模式选择性地限制桨距角。该系统包括具有前后室56,58，输油轴承（OTB）70和细止动套环86的致动器45.细止动套环包括与OTB和前室在流体连通的第一通道88 基于地面的操作模式，以及在基于飞行的操作模式期间与OTB和前进腔室流体连通的第二流体通道90。

54. 发明授权

EP1881176B1 An engine arrangement 有权转让
标题翻译：发动机位置
公开(公告)号：EP1881176B1
公开(公告)日：2017-03-01
申请号：EP07252526.4
申请日：2007-06-21
申请人： Rolls-Royce plc
发明人： Beaven, David Michael
IPC分类号： F02C3/067 , F02K3/072
CPC分类号： F01D1/26 , B64C11/48 , B64D2027/005 , F02C3/067 , F02C9/58 , F02K3/072 , F05D2220/324 , F05D2220/325 , F05D2260/40311 , Y02T50/66

55. 发明公开

EP3102487A1 PALE POUR UNE HELICE DE TURBOMACHINE, NOTAMMENT A SOUFFLANTE NON CARENEE, HELICE ET TURBOMACHINE COMPRENANT UNE TELLE PALE 有权
标题翻译： BLADE用于涡轮螺旋桨发动机，尤其是道具扇发动机，螺旋桨和涡轮发动机，这种铲
公开(公告)号：EP3102487A1
公开(公告)日：2016-12-14
申请号：EP15704355.5
申请日：2015-01-22
申请人： Safran Aircraft Engines
发明人： VION, Laurence, Francine , FERNANDO, Rasika , JODET, Norman, Bruno, André
IPC分类号： B64C11/18 , F01D5/14
CPC分类号： B64C11/18 , B64C11/48 , B64D27/10 , B64D2027/005 , F01D5/145 , F01D5/148 , F05D2220/36 , F05D2240/303 , F05D2260/961 , F05D2270/62 , F05D2270/64 , F05D2270/65 , Y02T50/66 , Y02T50/673
摘要： The invention relates to a blade (11A) for a turbine engine propeller, in particular a propfan engine, comprising a protruding part (16) on the leading edge (17) thereof, characterised in that said blade comprises means for controlling the position of the protruding part along the leading edge thereof.

56. 发明公开

EP2483556A4 ELECTRICAL POWER GENERATION APPARATUS FOR CONTRA- ROTATING OPEN-ROTOR AIRCRAFT PROPULSION SYSTEM 审中-实审
标题翻译：发电装置用于与对面开式转子一种平面驱动系统
公开(公告)号：EP2483556A4
公开(公告)日：2016-09-14
申请号：EP10820931
申请日：2010-09-02
申请人： ROLLS ROYCE NAM TECH INC
发明人： BLACKWELDER MARK J , ALT JOHN TIMOTHY , GAGNE STEVEN , VETTERS DANIEL KENT
IPC分类号： F03D9/00 , B64C11/48 , B64D15/12 , B64D27/00 , B64D27/02 , F02K3/072 , H02K7/18
CPC分类号： H02K7/1823 , B64C11/48 , B64D15/12 , B64D2027/005 , B64D2027/026 , F02K3/072 , F05D2220/768 , Y02T50/66 , Y02T50/671
摘要： An electrical power generation apparatus is embedded in a contra-rotating propulsion system that includes overlapping first and second shafts operatively connected for counter-rotation about a common axis. The electrical power generation apparatus includes a winding mounted to one of the shafts and a field array mounted to the other of the shafts adjacent to the winding. Relative rotation of the winding and the field array induces electrical current in the winding.

57. 发明授权

EP2436596B1 Pitch change apparatus for counter-rotating propellers 有权
标题翻译：反转螺旋桨的变桨装置
公开(公告)号：EP2436596B1
公开(公告)日：2016-07-13
申请号：EP11183355.4
申请日：2011-09-29
申请人： General Electric Company
发明人： Glynn, Christopher Charles , Zatorski, Darek Tomasz , Yeager, Donald Scott , Dinsmore, Nicholas Rowe , Menard, Jeffrey Raymond , Miller, Brandon Wayne
IPC分类号： B64C11/38 , B64C11/48 , B64D27/02
CPC分类号： B64C11/38 , B64C11/48 , B64D2027/005 , B64D2027/026 , Y02T50/66

58. 发明公开

EP3002436A1 METHOD AND SYSTEM FOR MODEL BASED CONTROL FOR VARIABLE PITCH FAN ENGINES AND TURBO-SHAFT, TURBO-PROPELLER ENGINES 审中-公开
标题翻译：方法和系统可调节风扇电机及TURBOWELLEN-和涡轮螺旋桨发动机基于模型的控制
公开(公告)号：EP3002436A1
公开(公告)日：2016-04-06
申请号：EP15187117.5
申请日：2015-09-28
申请人： General Electric Company
发明人： LU, Manxue , CARPENTER, R. Sheldon
IPC分类号： F02C9/58
CPC分类号： B64C11/305 , B64D27/10 , B64D2027/005 , F02C9/58 , F05D2270/02 , F05D2270/052 , F05D2270/13 , Y02T50/66
摘要： A method and control system (10) for an aircraft engine comprising a gas turbine driving a fan propeller with a mechanical gear-train and a dedicated pitch change mechanism for the fan propeller includes a fuel flow signal input (20); a pitch change mechanism signal input (22); a controlled plant (28) for relating a pitch change mechanism pitch angle (BetaP) and a fuel flow (Wf) to at least two controlled outputs (24, 26) and a set of constraints. A decoupling control (34) decoupling the controlled plant (28) and/or the constraints into two separate single-input single-output (SISO) control loops for the first and second controlled outputs (24, 26) and a decoupling control decoupling the constraints from the decoupled controlled outputs and the constraints from one another provide gas turbine and fan propeller coordinate control while coordinately controlling constraints and outputs (24, 26). A feedforward control can compensate the load change effect on engine speed and fan propeller rotor speed control.
摘要翻译：在飞机发动机，其包括燃气涡轮机驱动的风扇螺旋桨有机械齿轮系和一个专用的音高改变机构用于风扇螺旋桨的方法和控制系统（10）包括燃料流量信号输入端（20）; 俯仰改变机构的输入信号（22）; 受控设备（28），用于与一个音高改变机构的桨距角（测试版p）和燃料流率（Wf）到至少两个受控输出（24,26）和一组约束。去耦控制（34）去耦的控制植物（28）和/或约束成两个单独的单输入单输出（SISO）控制回路用于第一和第二控制输出（24,26）和一个解耦控制解耦从去耦受控输出限制和约束彼此提供燃气轮机和风扇螺旋桨坐标控制，同时协调控制限制和输出（24,26）。前馈控制可以补偿发动机转速和风扇螺旋桨转子速度控制负载变化的影响。

59. 发明公开

EP2557033A3 Modular counter rotating propeller system 有权转让
标题翻译：模块化反向旋转的螺旋桨系统
公开(公告)号：EP2557033A3
公开(公告)日：2015-11-11
申请号：EP12179560.3
申请日：2012-08-07
申请人： Hamilton Sundstrand Corporation
发明人： Perkinson, Robert H.
IPC分类号： B64C11/48 , B64C11/30
CPC分类号： B64C11/48 , B64C11/306 , B64D2027/005 , Y02T50/66
摘要： A self-contained counter rotating turbo prop system (14) is driven by a gas turbine engine (10) through a reduction gearbox (12). A gear train housed separate from the reduction gearbox (12) provides the counter-rotation of a first and second pluralities of propeller blades (18,20). The entire counter-rotating propeller system (14) is disposed within cowlings (16A,16B) and is separate from the gas turbine engine (10) and reduction gearbox (12). The counter rotating propeller system (14) includes a collective blade angle actuation system (55) that provides for adjustment of blade angle of both the first and second plurality of propeller blades (18,20) with a single actuator.

60. 发明授权

EP2610164B1 Rear fuselage with a shield for an aircraft with fuselage-mounted engines and method for determining the area of the shield 有权
标题翻译：用于确定所述屏蔽罩的表面，用于与机身安装的发动机的飞机的屏蔽后机身部分，和方法
公开(公告)号：EP2610164B1
公开(公告)日：2015-10-28
申请号：EP11382409.8
申请日：2011-12-28
申请人： Airbus Operations S.L.
发明人： Guillemaut, Julien , Folch Cortés, Diego , Martino Gonzalez, Esteban , Goya Abaurrea, Pablo , Vinué Santolalla, Eduardo
IPC分类号： B64D27/14 , B64C1/10 , B64C1/06
CPC分类号： B64D45/00 , B64C1/06 , B64C1/10 , B64D27/02 , B64D27/14 , B64D27/20 , B64D2027/005 , Y02T50/66

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